摘要
利用捷联导引头和速率陀螺的测量信息,得到旋转导弹实现比例导引制导律所需要的制导信号。定义了相关的坐标系,给出了各坐标系之间的关系,得到了惯性系下视线角的计算公式,进一步给出了惯性系下视线角速度的计算公式,最后得出了旋转导弹比例导引制导律的实现方法。
The guidance signal of proportional navigation law for rolling missiles is derived through the metrical information of strapdown seekers and rate gyros. The correlative coordinate systems are defined and the relationships between them are presented. The calculation formulas of angles of the line of sight in the inertial frame and the calculation formulas of angular rate are deduced and obtained consequently. Finally the implemental means of proportional navigation guidance law for rolling missiles is acquired.
出处
《现代防御技术》
北大核心
2009年第5期45-48,共4页
Modern Defence Technology
关键词
旋转导弹
捷联导引头
比例导引
rotative missile
strapdown seeker
proportional guidance
